Establishing viable fault management strategies for distributed electrical propulsion aircraft

Research output: Contribution to conferencePaper

Abstract

Electrical propulsion has the potential to increase aircraft performance. However, this will require the design and development of an appropriate aircraft electrical system to power the propulsor motors. In order to protect this system against electrical faults, which have the potential to threaten the safety of the aircraft, a robust fault management strategy (FMS) is required. The FMS will comprise aspects of system design such as redundancy, reliability and reconfiguration and will rely on a range of protection devices deployed on the electrical system to intercept and manage faults. The electrical architecture will be shaped by the FMS as this will determine the optimal configuration to enable security of supply. The protection system is integral to the system design. Hence it must to be considered from the outset, as part of the wider aircraft concept development. This paper presents a robust framework to develop the optimal FMS for an electrical propulsion aircraft, which is subject to all the relevant aircraft constraints and incorporates the available protection devices for a chosen aircraft for a given developmental timeframe. A case study is then presented in which this protection design methodology is applied to the NASA STARC-ABL aircraft concept in order to demonstrate that the available protection for an electrical propulsion aircraft defines the possible electrical architectures.

Conference

ConferenceInternational Society of Air Breathing Engines
Abbreviated titleISABE
CountryUnited Kingdom
CityManchester
Period3/09/178/09/17
Internet address

Fingerprint

Aircraft propulsion
Aircraft
Systems analysis
Propulsion
Redundancy
NASA

Keywords

  • hybrid electric propulsion aircraft
  • electrical protection systems
  • electrical power system fault management
  • fault management
  • aircraft propulsion

Cite this

Flynn, M-C., Jones, C. E., Norman, P. J., & Galloway, S. J. (2017). Establishing viable fault management strategies for distributed electrical propulsion aircraft. Paper presented at International Society of Air Breathing Engines, Manchester, United Kingdom.
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title = "Establishing viable fault management strategies for distributed electrical propulsion aircraft",
abstract = "Electrical propulsion has the potential to increase aircraft performance. However, this will require the design and development of an appropriate aircraft electrical system to power the propulsor motors. In order to protect this system against electrical faults, which have the potential to threaten the safety of the aircraft, a robust fault management strategy (FMS) is required. The FMS will comprise aspects of system design such as redundancy, reliability and reconfiguration and will rely on a range of protection devices deployed on the electrical system to intercept and manage faults. The electrical architecture will be shaped by the FMS as this will determine the optimal configuration to enable security of supply. The protection system is integral to the system design. Hence it must to be considered from the outset, as part of the wider aircraft concept development. This paper presents a robust framework to develop the optimal FMS for an electrical propulsion aircraft, which is subject to all the relevant aircraft constraints and incorporates the available protection devices for a chosen aircraft for a given developmental timeframe. A case study is then presented in which this protection design methodology is applied to the NASA STARC-ABL aircraft concept in order to demonstrate that the available protection for an electrical propulsion aircraft defines the possible electrical architectures.",
keywords = "hybrid electric propulsion aircraft, electrical protection systems, electrical power system fault management, fault management, aircraft propulsion",
author = "Marie-Claire Flynn and Jones, {Catherine E.} and Norman, {Patrick J.} and Galloway, {Stuart J.}",
year = "2017",
month = "9",
day = "3",
language = "English",
note = "International Society of Air Breathing Engines, ISABE ; Conference date: 03-09-2017 Through 08-09-2017",
url = "https://isabe2017.org/",

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Flynn, M-C, Jones, CE, Norman, PJ & Galloway, SJ 2017, 'Establishing viable fault management strategies for distributed electrical propulsion aircraft' Paper presented at International Society of Air Breathing Engines, Manchester, United Kingdom, 3/09/17 - 8/09/17, .

Establishing viable fault management strategies for distributed electrical propulsion aircraft. / Flynn, Marie-Claire; Jones, Catherine E.; Norman, Patrick J.; Galloway, Stuart J.

2017. Paper presented at International Society of Air Breathing Engines, Manchester, United Kingdom.

Research output: Contribution to conferencePaper

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T1 - Establishing viable fault management strategies for distributed electrical propulsion aircraft

AU - Flynn, Marie-Claire

AU - Jones, Catherine E.

AU - Norman, Patrick J.

AU - Galloway, Stuart J.

PY - 2017/9/3

Y1 - 2017/9/3

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AB - Electrical propulsion has the potential to increase aircraft performance. However, this will require the design and development of an appropriate aircraft electrical system to power the propulsor motors. In order to protect this system against electrical faults, which have the potential to threaten the safety of the aircraft, a robust fault management strategy (FMS) is required. The FMS will comprise aspects of system design such as redundancy, reliability and reconfiguration and will rely on a range of protection devices deployed on the electrical system to intercept and manage faults. The electrical architecture will be shaped by the FMS as this will determine the optimal configuration to enable security of supply. The protection system is integral to the system design. Hence it must to be considered from the outset, as part of the wider aircraft concept development. This paper presents a robust framework to develop the optimal FMS for an electrical propulsion aircraft, which is subject to all the relevant aircraft constraints and incorporates the available protection devices for a chosen aircraft for a given developmental timeframe. A case study is then presented in which this protection design methodology is applied to the NASA STARC-ABL aircraft concept in order to demonstrate that the available protection for an electrical propulsion aircraft defines the possible electrical architectures.

KW - hybrid electric propulsion aircraft

KW - electrical protection systems

KW - electrical power system fault management

KW - fault management

KW - aircraft propulsion

M3 - Paper

ER -

Flynn M-C, Jones CE, Norman PJ, Galloway SJ. Establishing viable fault management strategies for distributed electrical propulsion aircraft. 2017. Paper presented at International Society of Air Breathing Engines, Manchester, United Kingdom.